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首页> 外文会议>ASME(American Society of Mechanical Engineers) Turbo Expo vol.6 pt.A; 20050606-09; Reno-Tahoe,NV(US) >ADVANCED TURBINE AERODYNAMIC DESIGN UTILIZING A FULL STAGE CFD
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ADVANCED TURBINE AERODYNAMIC DESIGN UTILIZING A FULL STAGE CFD

机译：利用全阶段CFD进行先进的涡轮气动设计

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Gas turbines for power generation are required to operate more efficiently than ever before for both economic and environmental reasons. Because of this situation, an advanced multistage turbine design and optimization system is required to improve upon existing turbine designs where viscous CFD codes had already been applied on a single row or single stages basis. An advanced CFD code for multistage design applications has been developed at Mitsubishi Heavy Industries (MHI) and has been applied to the redesign of a four stage single shaft turbine. The front 3 stages of the turbine are highly cooled using about 20% cooling air. The outstanding performance of this redesigned turbine has been demonstrated at MHI's engine test facility This paper focuses on the customization of the Denton code for industrial usage, the validation of the customized code employing experimental data, and finally the use of the code in executing a successful redesign. Code development and validation are discussed in terms of prediction accuracy for the basic aerodynamic design parameters such as exit flow angle and cascade losses. Through-flow design parameters such as pressure ratio and reaction of each stage are also addressed. Especially important in modem high temperature turbines is the location and distribution of cooling and leakage air being introduced into the main gas-path. The proper treatment of these flows is very important because of the mixing losses and the temperature migration downstream. These important considerations in any analysis approach are discussed and it is shown how they are treated in the customized CFD code. Consistency between the customized CFD code and other parts of the existing aerodynamic design procedure are carefully examined. This is important because aerodynamic parameters have different modeling fidelities in the different parts of the design system. Computer execution times are a very important consideration when utilizing advanced CFD codes. This issue is addressed from the perspective of an industrial design organization. In validating the customized code, special attention was placed on tip clearance leakage flow behavior and seal air migration from the hub wall. Local changes of total pressure and temperature distributions affect the local velocity triangles and local static pressure distributions on the airfoil and end-wall surfaces. Airfoil section geometry and three-dimensional stacking to maximize the turbine efficiency are also considered and discussed. The validated code was subsequently used to execute a redesign of a large frame industrial turbine. This is discussed in some detail. The redesigned turbine has completed full scale engine testing and has been shown to have met all design goals. The CFD predictions are compared with special measurements taken in the engine such as the inter-stage span-wise total pressure and temperature distributions as well as the efficiency trend versus engine load. These comparisons prove the capability of the advanced multistage CFD code.
机译：出于经济和环境方面的原因，用于发电的燃气轮机需要比以往更有效地运行。由于这种情况，需要先进的多级涡轮机设计和优化系统来改进现有的涡轮机设计，在现有的涡轮机设计中，粘性CFD代码已在单行或单级基础上应用。三菱重工（MHI）已开发出适用于多级设计应用程序的高级CFD代码，并已用于重新设计四级单轴涡轮机。涡轮机的前三级使用约20％的冷却空气进行高度冷却。这种重新设计的涡轮机的出色性能已在三菱重工的发动机测试设施中得到了证明。本文着重于为工业用途定制Denton代码，利用实验数据对定制代码进行验证，最后将代码用于成功执行重新设计。根据基本的空气动力学设计参数（例如出口流角和叶栅损失）的预测准确性，讨论了代码的开发和验证。还讨论了通流设计参数，例如每个阶段的压力比和反应。在现代高温涡轮机中，特别重要的是将冷却和泄漏空气的位置和分布引入主气体通道。由于混合损失和下游的温度迁移，对这些流进行适当的处​​理非常重要。讨论了任何分析方法中的这些重要注意事项，并显示了如何在自定义CFD代码中对其进行处理。仔细检查了自定义CFD代码与现有空气动力学设计程序其他部分之间的一致性。这很重要，因为空气动力学参数在设计系统的不同部分具有不同的建模逼真度。使用高级CFD代码时，计算机执行时间是非常重要的考虑因素。从工业设计组织的角度解决了此问题。在验证定制代码时，特别注意了叶尖间隙泄漏流动行为和密封空气从轮毂壁的迁移。总压力和温度分布的局部变化会影响翼型和端壁表面上的局部速度三角形和局部静压力分布。还考虑并讨论了翼型截面的几何形状和三维堆叠以最大化涡轮效率。经过验证的代码随后用于执行大型工业涡轮机的重新设计。对此进行了详细讨论。经过重新设计的涡轮机已经完成了全尺寸发动机测试，并且已证明满足所有设计目标。将CFD预测值与发动机中进行的特殊测量（例如级间跨度总压力和温度分布以及效率趋势与发动机负载）进行比较。这些比较证明了高级多级CFD代码的功能。

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